Deflector blade of variable camber

Abstract

A deflector blade suitable for directing jet exhaust of an aircraft rearward or downward has leading and trailing edge portions and an intermediate portion interposed between the edge portions. The three portions and a crank constitute a four-bar linkage connected by four pivots having parallel axes of which a first connects the leading edge portion and intermediate portion, the second connects the crank and the leading edge portion, the third connects the intermediate and trailing edge portions, and the fourth connects the trailing edge portion and the crank. The line connecting the axes of the first and third pivots intersects the connecting line defined by the axes of the second and fourth pivots. When the crank is moved about the axis of the second pivot, the blade is moved between a neutral position for rearward jet exhaust and one of positive angle of deflection in which the jet exhaust is directed downward for providing lift to the aircraft.

What is claimed is: 
     
       1. A deflector blade of variable camber comprising: a. a leading edge portion;   b. a trailing edge portion;   c. an intermediate portion interposed between said leading and trailing edge portions;   d. a crank member;   e. a first pivot hingedly connecting said leading edge portion to said intermediate portion;   f. a second pivot hingedly connecting said crank member to said leading edge portion;   g. a third pivot hingedly connecting said intermediate portion to said trailing edge portion,   h. a fourth pivot hingedly connecting said trailing edge portion to said crank member,   
     
     
       1.  said first, second, third, and fourth pivots having respective spaced, parallel axes, 2. the axes of said first and third pivots defining a connecting line intersecting the connecting line defined by the axes of said second and fourth pivots in a plane perpendicular to said axes,   3. a part of said crank member extending from said second pivot beyond said fourth pivot; and   i. actuating means including an actuating member secured to said part of said crank member for angularly moving said crank member about the axis of said second pivot.   
     
     
       2. A blade as set forth in claim 1, wherein said portions jointly define a top face and a bottom face of said blade, said intermediate portion defining a gap with at least one of said edge portions, said gap extending between said faces, the blade further comprising a top cover and a bottom cover respectively superimposed on said faces and closing said gap. 
     
     
       3. A blade as set forth in claim 2, wherein said third pivot is confined in said gap. 
     
     
       4. A blade as set forth in claim 2, further comprising fastening means fixedly fastening respective parts of said bottom cover to said edge portions, said bottom cover movably covering the bottom face of said intermediate portion. 
     
     
       5. A blade as set forth in claim 2, further comprising fastening means fixedly fastening a portion of said top cover to said leading edge portion, and securing means securing another portion of said top cover to said trailing edge portion. 
     
     
       6. A blade as set forth in claim 1, wherein said actuating means include means for moving said trailing edge portion relative to said leading edge portion through an angle of at least 60°. 
     
     
       7. A blade as set forth in claim 6, wherein said angle is about 90°. 
     
     
       8. An aircraft comprising: a. an airframe;   b. a source of a stream of gas on said airframe; and   c. guide means for ejecting said stream from said source in a plurality of directions relative to said airframe, said guide means including at least one deflector blade having 1. a leading edge portion fixedly mounted on said airframe in said stream of gas,   2. a trailing edge portion;   3. an intermediate portion interposed between said leading and trailing edge portions,   4. a crank member,   5. a first pivot hingedly connecting said leading edge portion to said intermediate portion,   6. a second pivot hingedly connecting said crank member to said leading edge portion,   7. a third pivot hingedly connecting said intermediate portion to said trailing edge portion,   8. a fourth pivot hingedly connecting said trailing edge portion to said crank member, i. said first, second, third, and fourth pivots having respective spaced, parallel axes,   ii. the axes of said first and third pivots defining a connecting line intersecting the connecting line defined by the axes of said second and fourth pivots in a plane perpendicular to said axes,   iii. a part of said crank member extending from said second pivot beyond said fourth pivot, and     9. actuating means including an actuating member secured to said part of said crank member for angularly moving said crank member about the axis of said second pivot.     
     
     
       9. An aircraft as set forth in claim 8, wherein said guide means include a plurality of said deflector blades, the leading edge portions of said blades being spaced in said stream of gas transverse to the direction of said stream.